EH 1.0/9.0 (eh1090-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 1.0/9.0 (eh1090-il) Reynolds number: 100,000 Max Cl/Cd: 43.26 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh1090-il-100000.txt Download as CSV file: xf-eh1090-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EH 1.0/9.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5865 0.08901 0.08447 -0.0015 1.0000 0.1160
-8.250 -0.6059 0.08419 0.07974 -0.0077 1.0000 0.1196
-8.000 -0.6469 0.07949 0.07492 -0.0149 1.0000 0.1221
-7.750 -0.5730 0.06695 0.06276 -0.0153 1.0000 0.1349
-7.500 -0.6150 0.07143 0.06698 -0.0122 1.0000 0.1318
-6.750 -0.6265 0.04716 0.04109 -0.0175 1.0000 0.0694
-6.500 -0.6148 0.04116 0.03421 -0.0152 1.0000 0.0557
-6.250 -0.5980 0.03743 0.03016 -0.0139 1.0000 0.0548
-6.000 -0.5831 0.03368 0.02592 -0.0124 1.0000 0.0563
-5.750 -0.5640 0.03045 0.02238 -0.0112 1.0000 0.0574
-5.500 -0.5421 0.02760 0.01909 -0.0097 1.0000 0.0573
-5.250 -0.5191 0.02518 0.01641 -0.0085 1.0000 0.0591
-5.000 -0.4949 0.02320 0.01424 -0.0073 1.0000 0.0625
-4.750 -0.4708 0.02143 0.01225 -0.0061 1.0000 0.0697
-4.500 -0.4477 0.02009 0.01079 -0.0049 1.0000 0.0816
-4.250 -0.4269 0.01843 0.00936 -0.0036 1.0000 0.1012
-4.000 -0.4072 0.01703 0.00811 -0.0018 1.0000 0.1360
-3.750 -0.3899 0.01567 0.00715 0.0000 1.0000 0.1913
-3.500 -0.3753 0.01414 0.00636 0.0021 1.0000 0.2912
-3.250 -0.3691 0.01223 0.00603 0.0062 1.0000 0.5631
-3.000 -0.3552 0.01186 0.00636 0.0113 1.0000 0.7733
-2.750 -0.3301 0.01219 0.00670 0.0143 1.0000 0.8652
-2.500 -0.2763 0.01285 0.00709 0.0119 1.0000 0.9261
-2.250 -0.1776 0.01337 0.00709 0.0000 1.0000 0.9583
-2.000 -0.0804 0.01326 0.00658 -0.0131 1.0000 0.9855
-1.750 -0.0182 0.01280 0.00590 -0.0206 1.0000 1.0000
-1.500 -0.0041 0.01259 0.00566 -0.0193 1.0000 1.0000
-1.250 0.0063 0.01246 0.00554 -0.0173 1.0000 1.0000
-1.000 0.0066 0.01249 0.00560 -0.0138 1.0000 1.0000
-0.750 -0.0166 0.01281 0.00595 -0.0071 1.0000 1.0000
-0.500 0.0412 0.01291 0.00598 -0.0140 0.9843 1.0000
-0.250 0.1084 0.01285 0.00585 -0.0222 0.9667 1.0000
0.000 0.1700 0.01268 0.00565 -0.0290 0.9444 1.0000
0.250 0.2201 0.01251 0.00544 -0.0333 0.9165 1.0000
0.500 0.2539 0.01242 0.00528 -0.0340 0.8857 1.0000
0.750 0.2759 0.01243 0.00522 -0.0325 0.8538 1.0000
1.000 0.2958 0.01249 0.00519 -0.0305 0.8250 1.0000
1.250 0.3147 0.01259 0.00521 -0.0283 0.7986 1.0000
1.500 0.3337 0.01271 0.00523 -0.0262 0.7742 1.0000
1.750 0.3533 0.01286 0.00532 -0.0243 0.7495 1.0000
2.000 0.3735 0.01304 0.00542 -0.0226 0.7262 1.0000
2.250 0.3942 0.01322 0.00554 -0.0208 0.7051 1.0000
2.500 0.4153 0.01343 0.00572 -0.0194 0.6823 1.0000
2.750 0.4367 0.01364 0.00586 -0.0178 0.6619 1.0000
3.000 0.4583 0.01387 0.00608 -0.0165 0.6400 1.0000
3.250 0.4802 0.01412 0.00626 -0.0151 0.6201 1.0000
3.500 0.5023 0.01438 0.00657 -0.0138 0.5985 1.0000
3.750 0.5246 0.01464 0.00678 -0.0125 0.5789 1.0000
4.000 0.5469 0.01492 0.00710 -0.0113 0.5571 1.0000
4.250 0.5694 0.01521 0.00735 -0.0100 0.5370 1.0000
4.500 0.5917 0.01549 0.00767 -0.0087 0.5142 1.0000
4.750 0.6140 0.01577 0.00801 -0.0075 0.4918 1.0000
5.000 0.6364 0.01607 0.00829 -0.0062 0.4695 1.0000
5.250 0.6588 0.01640 0.00871 -0.0050 0.4461 1.0000
5.500 0.6810 0.01673 0.00908 -0.0038 0.4218 1.0000
5.750 0.7025 0.01698 0.00937 -0.0024 0.3932 1.0000
6.000 0.7229 0.01712 0.00948 -0.0008 0.3585 1.0000
6.250 0.7419 0.01721 0.00966 0.0007 0.3115 1.0000
6.500 0.7605 0.01758 0.00997 0.0022 0.2511 1.0000
6.750 0.7679 0.01996 0.01136 0.0046 0.1111 1.0000
7.000 0.7782 0.02240 0.01341 0.0069 0.0738 1.0000
7.250 0.7940 0.02413 0.01511 0.0087 0.0609 1.0000
7.500 0.8130 0.02581 0.01688 0.0104 0.0548 1.0000
7.750 0.8327 0.02823 0.01919 0.0117 0.0508 1.0000
8.000 0.8552 0.03079 0.02196 0.0129 0.0486 1.0000
8.250 0.8751 0.03280 0.02430 0.0142 0.0450 1.0000
8.500 0.8939 0.03519 0.02701 0.0153 0.0425 1.0000
8.750 0.9102 0.03832 0.03051 0.0167 0.0420 1.0000
9.000 0.9211 0.04192 0.03464 0.0184 0.0423 1.0000
9.250 0.9252 0.04606 0.03935 0.0203 0.0434 1.0000
9.500 0.9239 0.05044 0.04421 0.0221 0.0447 1.0000
9.750 0.9179 0.05485 0.04901 0.0235 0.0459 1.0000
10.000 0.9078 0.05925 0.05369 0.0247 0.0471 1.0000
10.250 0.8951 0.06328 0.05791 0.0257 0.0480 1.0000
10.500 0.8802 0.06750 0.06225 0.0261 0.0488 1.0000
10.750 0.8779 0.07181 0.06669 0.0260 0.0511 1.0000
11.000 0.8488 0.07666 0.07172 0.0227 0.0514 1.0000
11.250 0.8163 0.08400 0.07919 0.0160 0.0517 1.0000
11.500 0.7106 0.08466 0.08008 0.0150 0.0495 1.0000
11.750 0.6926 0.09230 0.08781 0.0107 0.0508 1.0000
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Polar data table (+)
Polar graphs
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